U.S. patent application number 12/223888 was filed with the patent office on 2010-03-04 for force level control for an energy absorber for aircraft.
This patent application is currently assigned to Airbus Deutschland GmbH. Invention is credited to Michael Demary, Michael Harriehausen, Dirk Humfeldt, Jan Schroder, Martin Sperber.
Application Number | 20100051401 12/223888 |
Document ID | / |
Family ID | 38329526 |
Filed Date | 2010-03-04 |
United States Patent
Application |
20100051401 |
Kind Code |
A1 |
Humfeldt; Dirk ; et
al. |
March 4, 2010 |
FORCE LEVEL CONTROL FOR AN ENERGY ABSORBER FOR AIRCRAFT
Abstract
A force level control for an energy absorber is provided for
aircraft, and includes an adjustment element and a housing, whereby
via the adjustment element, a bending radius of the energy absorber
element is continuously adjustable in the housing.
Inventors: |
Humfeldt; Dirk; (Hamburg,
DE) ; Harriehausen; Michael; (Hamburg, DE) ;
Schroder; Jan; (Hamburg, DE) ; Sperber; Martin;
(Monchengladbach, DE) ; Demary; Michael;
(Meckenheim, DE) |
Correspondence
Address: |
LERNER, DAVID, LITTENBERG,;KRUMHOLZ & MENTLIK
600 SOUTH AVENUE WEST
WESTFIELD
NJ
07090
US
|
Assignee: |
Airbus Deutschland GmbH
Hamburg
DE
|
Family ID: |
38329526 |
Appl. No.: |
12/223888 |
Filed: |
January 31, 2007 |
PCT Filed: |
January 31, 2007 |
PCT NO: |
PCT/EP2007/000825 |
371 Date: |
November 10, 2009 |
Related U.S. Patent Documents
|
|
|
|
|
|
Application
Number |
Filing Date |
Patent Number |
|
|
60773760 |
Feb 15, 2006 |
|
|
|
Current U.S.
Class: |
188/371 |
Current CPC
Class: |
B60R 22/28 20130101;
B64D 25/04 20130101; F16F 7/128 20130101; B64C 1/062 20130101; F16F
7/123 20130101 |
Class at
Publication: |
188/371 |
International
Class: |
F16F 7/12 20060101
F16F007/12 |
Foreign Application Data
Date |
Code |
Application Number |
Feb 15, 2006 |
DE |
10 2006 007 028.3 |
Claims
1. A force level control for an energy absorber for an aircraft,
the force level control comprising: a housing; an adjustment
element; and a cover plate; wherein the energy absorber has an
energy absorber element for absorption of an acceleration energy by
plastic deformation; wherein the plastic deformation of the energy
absorber element takes place within the housing; wherein via the
adjustment element, a bending radius of the energy absorber element
is continuously adjustable in the housing; and wherein the cover
plate is, by actuation of the adjustment element, displaceable in
the direction of the energy absorber element, so that the energy
absorber element runs along a contact surface of the cover
plate.
2. The force level control of claim 1, further comprising: a second
adjustment element for displacing the cover plate and; wherein the
second adjustment element is actuatable independently from the
first adjustment element.
3. The force level control of claim 1, wherein the cover plate has
a contact surface that is formed such that the energy absorber
element bends in the area of the contact surface upon actuation of
the adjustment element.
4. The force level control of claim 1, further comprising: a second
energy absorber element; wherein the housing includes a first cover
plate, a second cover plate and a fixed support for the second
energy absorber element and the first energy absorber element.
5. The force level control of claim 1, and wherein the first energy
absorber element has a longitudinal slit; wherein the housing
further has an intermediate wall, which is mounted in the region of
the slit.
6. The force level control of claim 1, further comprising: a first
attachment region; and a second attachment region; wherein the
first attachment region is designed for attachment of the energy
absorber to a primary structure of the aircraft; and wherein the
second attachment region is designed for attachment of the energy
absorber to an inboard device.
7. The force level control of claim 1, wherein the attachment of
the holder to the primary structure or to the inner device is by
one or more of screws, rivets, or self-locking locking pins.
8. The force level control of claim 1, wherein the energy absorber
has an energy absorption direction; and wherein an energy
absorption occurs through the energy absorber upon exceeding a
minimal force, which acts in the direction of the energy absorption
direction.
9. (canceled)
Description
This application claims the benefit of German Patent Application
No. 10 2006 007 028.3 filed Feb. 15, 2006, and of U.S. Provisional
Application No. 60173,760. filed Feb. 15, 2006, the disclosures of
which are hereby incorporated herein by reference.
FIELD OF THE INVENTION
[0001] The present invention relates to energy absorbers for
aircraft. In particular, the present invention relates to a force
level control for an energy absorber for an aircraft and the use of
such a force level control energy absorber in an aircraft.
TECHNOLOGICAL BACKGROUND OF THE INVENTION
[0002] In aircraft, holders or attachment elements for holding and
attaching inboard devices, such as ceiling liners, overhead bins,
or monuments, are used. In the case of fixed attachment elements it
is often disadvantageous, in particular in the even of intense
accelerations, such as those that can occur in the event of severe
turbulence or for example, also with an emergency landing, that the
resulting acceleration forces are transmitted directly from the
primary structure of the aircraft over the holder to the attached
inboard device. Likewise, all forces or accelerations acting on the
inboard device are transferred directly via the holder or the
holder system to the aircraft structure.
[0003] Known holders and the inboard devices attached thereto may
be statically dimensioned on the basis of static load or maximum
service loads. A breakdown of the holder, such as for example, by
breaking or bursting out from the inboard device based on excessive
acceleration forces may occur, which may lead to damage to the
holder, the inboard device, or the primary structure of the
aircraft and further, may endanger or injure the passengers or lead
to impairment with a possible evacuation.
[0004] If the weight of the inboard devices changes (for example,
based on load), then the occurring forces and loads may change.
[0005] It is an object of the present invention to provide a force
level control for an energy absorber for aircraft, which provides a
flexible adjustment of the force level.
[0006] According to an exemplary embodiment of the present
invention, a force level control for an energy absorber for an
aircraft is provided, the force level control including a housing
and an adjustment element, wherein the energy absorber includes an
energy absorber element for absorption of an acceleration energy
resulting by plastic deformation, wherein the plastic deformation
of the energy absorber element takes place within the housing and
wherein via the adjustment element, a bending radius of the energy
absorber element in the housing is continuously adjustable.
[0007] Thus, a flexible, individually adjustable force level
regulation may be provided, which may be adjustable simply for the
current load.
[0008] According to an exemplary embodiment of the present
invention, the force level control further includes a cover plate,
which is displaceable by actuation of the adjustment element in the
direction of the energy absorber element, so that the energy
absorber element runs along a contact surface of the cover
sheet.
[0009] According to an exemplary embodiment of the present
invention, the force level control further includes a second
adjustment element for displacing the cover plate, whereby the
second adjustment element can be actuated independently from the
first adjustment element.
[0010] In this manner, progressive or declining force progressions
can be provided.
[0011] According to an exemplary embodiment of the present
invention, the cover plate has a contact surface, formed such that
the energy absorber element bends upon actuation of the adjustment
element in the area of the contact surface.
[0012] By means of the energy absorber elements, which are
integrated at least partially in the housing, the mechanical load
on the inboard device, which is connected by the energy absorber
with a primary structure of the aircraft, and which can be, for
example, a luggage bin mounted over the passengers, may be limited.
For example, the energy absorber can be designed for absorbing
acceleration energy resulting from movement of the aircraft. By
absorbing acceleration energies, the force transmissions from the
primary structure of the aircraft to the inboard device or from the
inboard device to the primary structure may be reduced. This may
lead to an increased passive safety in the cabin. In addition, by
using the energy absorber of the present invention with energy
absorber elements, the construction of the inboard device may be
designed in a material- or weight-savings manner, since the
maximally occurring mechanical loads are reduced. This may permit a
weight-optimization of all components involved on the load curve
(for example, inboard components, holder, and primary structure).
In addition, with a statically overruled system, a uniform load
distribution may be made possible, in particular with a structure
deformed by load.
[0013] By the use of multiple energy absorber elements, which are
arranged parallel to one another and lie flat on one another, the
force levels may be increased. At the same time, the existing space
may be better used and the differently positioned energy absorber
elements (for example, in the form of sheets) may affect a more
favorable force distribution on the deck layers by the now existing
two force lines.
[0014] Thus, with the energy absorber of the present invention,
crash impulses, like those that can occur with an emergency
landing, may be at least partially absorbed. The resulting force
impact accordingly is not transferred completely to the inboard
device, rather damped additionally or absorbed partially to a
defined force level, so that malfunction may be prevented.
[0015] By the principle of plastic deformation, it may further be
possible to absorb multiple crash impulses, and in the forward as
well as in the reverse direction. In other words, the energy
absorber may work in two directions (specifically, are extracted
from the housing and displaced into the housing) and thereby absorb
impacts in different directions.
[0016] According to a further embodiment of the present invention,
the second energy absorber element is inlaid in the first energy
absorber element.
[0017] In this manner, it may be ensured that an absorbed force is
distributed better on the housing.
[0018] According to a further embodiment of the present invention,
the energy absorber further includes a third energy absorber
element and a fourth energy absorber element, whereby the third
energy absorber element is inlaid in the fourth energy absorber
element and whereby the third energy absorber element and the
fourth energy absorber element are arranged adjacent to the first
energy absorber element and second energy absorber element, so that
both the energy absorber pairs are braced against one another with
a rolling motion. The outwardly acting forces may be reduced, such
that (with suitable construction) a separate housing may be
eliminated and may be integrated in the geometry (for example,
honeycomb plates with hatrack) to be attached.
[0019] Here, there may be no surfaces that are subject to
friction.
[0020] According to a further embodiment of the present invention,
the housing includes a first cover plate, a second cover plate, and
a fixed support for the second energy absorber element and the
first energy absorber element.
[0021] According to a further embodiment of the present invention,
the first energy absorber element has a longitudinal slit, whereby
the housing further has an intermediate wall, which is mounted in
the area of the slit.
[0022] By slitting the sheet and the division of the housing by the
intermediate walls into multiple chambers made possible thereby,
the maximum forces on the deck layers may be reduced
substantially.
[0023] According to a further embodiment of the present invention,
the energy absorber further includes a first attachment area and a
second attachment area, whereby the first attachment area is
designed for attachment of the energy absorber to the primary
structure and whereby the second attachment area is designed for
attachment of the energy absorber to the inboard device.
[0024] The attachment areas may make possible, for example, a
simple assembly. In this regard, the energy absorber first may be
fixedly mounted to a hull- or deck surface or to a support element
of the primary structure. Next, then, an inboard device element is
connected permanently at the second attachment area with the energy
absorber.
[0025] According to a further exemplary embodiment of the present
invention, the attachment of the energy absorber to the primary
structure or to the inboard device takes place by means of a force-
or positive-locking connection.
[0026] Therefore, an energy absorber may be provided, for example,
which can be mounted simply. The first attachment region, for
example, additionally may have a profile, for example, in the form
of a claw element, which is inserted onto a rectangular section of
a support. In this regard, the claw element can be designed, for
example, such that the energy absorber is held to the support with
this insertion, so that its fixed weight is held. For final
attachment of the energy absorber, the energy absorber then can be
fixed by means of screws, rivets or self-locking pins or similar
means to the support.
[0027] According to a further exemplary embodiment of the present
invention, the energy absorber further has an adjustment element.
The adjustment element may change the bending radius of the energy
absorber element and therewith, the lever arm. In this manner, a
change of the force level may be provided (variable constant
performance level as well as progressive or declining performance
is thus adjustable).
[0028] In this manner, the force progression may be freely adjusted
by continuous change of the cover plate distance.
[0029] In addition, the force-path progression may be adapted
individually by a contour adaptation of the cover plate. In
addition, the energy absorber itself may be structured or
contoured, in order to individually adjust a further adaptation of
the force-path progression.
[0030] For example, the cover plate may have a bulge or hump, so
that the energy absorber element can be forced to an additional
bending, which affects likewise the force level.
[0031] According to a further exemplary embodiment of the present
invention, the energy absorber has an energy absorption direction,
whereby first upon exceeding of a minimal force (force limiting),
which acts in the direction of the energy absorption direction, an
energy absorption occurs through the energy absorber.
[0032] The inner device (or the like) may be supported
substantially fixedly with correspondingly minimal load, so that it
may suitable for normal on-board operation. With increased load,
such as through an intense impact of force, a damping is
established, in which for example, the energy absorber is pulled in
the absorption direction from the housing (or is pushed into the
housing). In this manner, correspondingly intense force impacts are
effectively absorbed.
[0033] According to a further exemplary embodiment of the present
invention, the use of an energy absorber in an aircraft is
provided.
[0034] According to a further exemplary embodiment of the present
invention, a method for energy absorption in an aircraft is
provided, including a pulling out of a first energy absorber
element and a second energy absorber element from the housing, and
an absorption of an acceleration energy by plastic deformation of
the first energy absorber element and of the second energy absorber
element within the housing during the pulling out, whereby the
second energy absorber element is arranged parallel to the first
energy absorber element and lies flat on this.
[0035] Further objects and embodiments of the invention are
provided in the dependent claims.
[0036] Next, the invention will be described in greater detail with
regard to exemplary embodiments in reference to the drawings.
[0037] FIG. 1A shows a schematic cross-sectional representation of
the energy absorber.
[0038] FIG. 1B shows a schematic representation of the energy
absorber of FIG. 1A in plan view.
[0039] FIG. 2A shows a schematic cross-sectional representation of
an energy absorber.
[0040] FIG. 2B shows a further schematic cross-sectional
representation of the energy absorber of FIG. 2A.
[0041] FIG. 3A shows a schematic cross-sectional representation of
an energy absorber.
[0042] FIG. 3B shows a further schematic cross-sectional
representation of the energy absorber of FIG. 3A.
[0043] FIG. 4A shows a schematic cross-sectional representation of
a further energy absorber.
[0044] FIG. 4B shows a further schematic cross-sectional
representation of the energy absorber of FIG. 4A.
[0045] FIG. 5A shows a schematic cross-sectional representation of
an energy absorber.
[0046] FIG. 5B shows a further schematic cross-sectional
representation of the energy absorber of FIG. 5A.
[0047] FIG. 6A shows an energy absorber in a schematic
cross-sectional.
[0048] FIG. 6B shows a further schematic cross-sectional
representation of the energy absorber of FIG. 6A.
[0049] FIG. 6C shows a detail enlargement of a region of the energy
absorber of FIG. 6A.
[0050] FIG. 7A shows a schematic cross-sectional representation of
an energy absorber.
[0051] FIG. 7B shows a further schematic cross-sectional
representation of the energy absorber of FIG. 7A.
[0052] FIG. 8A shows a schematic cross-sectional representation of
a force level control for an energy absorber according to an
exemplary embodiment of the present invention.
[0053] FIG. 8B shows a further schematic cross-sectional
representation of the force level control of FIG. 8A.
[0054] FIG. 8C shows an exemplary force-path-progression of the
energy absorber according to the configuration of FIGS. 8A, 8B.
[0055] FIG. 8D shows the energy absorber of FIGS. 8A, 8B with an
actuated adjustment element.
[0056] FIG. 8E shows a corresponding force-path-progression of the
energy absorber according to the configuration of FIG. 8D.
[0057] FIG. 9A shows an energy absorber with an adjustment element
according to a further exemplary embodiment of the present
invention.
[0058] FIG. 9B shows a corresponding force-path-progression of the
energy absorber according to the configuration of FIG. 9A.
[0059] FIG. 9C shows the energy absorber of FIG. 9A with a
different actuated adjustment element.
[0060] FIG. 9D shows the corresponding force-path-progression of
the energy absorber according to the configuration of FIG. 9C.
[0061] FIG. 10A shows an energy absorber with an adjustment element
according to a further exemplary embodiment of the present
invention.
[0062] FIG. 10B shows the energy absorber of FIG. 10A in a further
cross-sectional representation.
[0063] FIG. 10C shows the corresponding force-path-progression of
the energy absorber according to the configuration of FIGS. 10A,
10B.
[0064] FIG. 10D shows the energy absorber of FIG. 10A with actuated
adjustment elements.
[0065] FIG. 10E shows the corresponding force-path-progression of
the energy absorber according to the configuration of FIG. 10D.
[0066] FIG. 11A shows an energy absorber with actuated adjustment
elements according to a further exemplary embodiment of the present
invention.
[0067] FIG. 11B shows the corresponding force-path-progression of
the energy absorber according to the configuration of FIG. 11A.
[0068] FIG. 11C shows a further energy absorber with actuated
adjustment elements according to a further exemplary embodiment of
the present invention.
[0069] FIG. 11D shows the force-path-progression of the energy
absorber according to the configuration of FIG. 11C.
[0070] In the following description of the figures, the same
reference numerals are used for the same or similar elements.
[0071] The representations in the figures are schematic and not to
scale.
[0072] FIG. 1A shows a schematic cross-sectional representation of
an energy absorber according to an exemplary embodiment of the
present invention. The energy absorber 100 has a lower housing
region 101 and an upper housing region 102, between which the
energy absorber element is mounted.
[0073] The energy absorber 100, in which this energy absorber
elements 1 are installed, is subdivided basically into so-called
single deckers with a plate or sheet or with multiple plates or
sheets placed in one another and so-called multiple decker with two
or more sheets running opposite to one another (which can comprises
respectively again multiple sheets placed in one another).
[0074] Thus, multiple sheets may be nested in one another, in order
to achieve for example an optimization of the cover layer load,
better volume use or increased force level.
[0075] In addition, the energy absorber 100 includes a fixed
support 103 for the energy absorber element 1 and force impact
points 105-112, 115.
[0076] FIG. 1B shows the energy absorber of FIG. 1A in a
representation rotated at 90.degree.. The upper housing part or
double-cover sheet 102 has a bore 113 for attachment, for example,
to the primary structure of the aircraft. The energy absorber
element 1 has a bore 114 for attachment, for example, to an inboard
device part of the aircraft. If a force acts now on the housing in
the direction of the arrow 116 and a force acts on the absorber
element 1 in the opposite direction1 17, then the absorber element
is pulled out from the housing by plastic deformation upon
exceeding a known minimal force. Thus, energy is absorbed.
[0077] The absorption functions also in the reverse direction, as
specifically the energy absorber element 1 is pressed into the
housing. The first impact points 105 to 112 and 115 serve on the
one hand for connection of the cover sheets 101, 102 and for
distribution of the occurring forces (symbolized by force line 118
and arrows 119, 120).
[0078] The structure shown in FIG. 1 represents the basic form of
the single decker. Here, the energy absorber element 1 is braced
against the cover layers 101, 102 and is transformed upon reaching
the trigger force.
[0079] FIGS. 2A, 2B shows cross-sectional representations of an
energy absorber according to a further exemplary embodiment of the
present invention. This structure is principally designed like the
structure in FIG. 1. By means of the slits of the sheet 1 and the
subdivision of the housing 102, 101 made possible in this manner by
intermediate walls 202 into multiple chambers, the forces may be
greatly reduced or uniformly distributed. Reference numeral 201
represents a slit in the sheet, in which an intermediate wall 202
runs.
[0080] FIGS. 3A, 3B show a further energy absorber according to a
further exemplary embodiment of the present invention in two
cross-sectional representations. This structure may be viewed as an
independent deformation principle. Since here, however, only one
energy absorber element 1 may be deformed, this structure is
attributed likewise to the single-decker. The sheet is passed
around multiple times around rollers 301, 302, 303, 304, 305, 306,
307. The rollers may be designed to be rotatable, in order to hold
the frictional effect at a minimum.
[0081] FIGS. 4A, 4B show an energy absorber according to a further
exemplary embodiment of the present invention, which belongs to the
structure "double decker".
[0082] Here, the first energy absorber element 1 is braced on-one
side against the cover layer 102. A second energy absorber element
3 is provided, which is braced on the other side against the lower
cover layer 101. The energy absorber elements 1, 3 are deformed
upon reaching the tripper force and roll against one another.
[0083] FIGS. 5A, 5B shows an energy absorber according to a further
exemplary embodiment of the present invention. This structure is
designed principally like the structure of FIG. 4. By the placement
of two or more sheets 1, 2 or 3, 4, the force level may be
increased. For example, larger loads may therefore be absorbed. At
the same time, one uses the space better and the differently
positioned sheets affect a favorable force distribution on the
cover layers 101, 102 through the now existing two force lines
118.
[0084] FIGS. 6A, 6B, 6C shows a further embodiment of the energy
absorber. Here, respectively, two (or more) sheets are placed in
one another (1, 2 or 3, 4 or 5, 6 or 7, 8). In addition, the
different groups of inlaid sheets are placed respectively over one
another. The sheet pair 1, 2 is braced with a rolling motion
against the sheet pair 3, 4 and the sheet pair 5, 6, is braced with
a rolling motion against the sheet pair 7, 8.
[0085] The structural space here is used very favorably. The
multiple sheets lying over one another acts by their arrangement
itself like cover sheets and may thus reduce the forces acting on
the cover layers 101, 102.
[0086] In addition, through the adjacent placement of such sheets,
the thickness of the energy absorber 100 (that is, the spacing of
both cover sheets 101, 102) with constant force progression may be
reduced. This may enable an integration of the energy absorber in a
sandwich plate, for example, which may result in turn in reduction
of the housing.
[0087] FIGS. 7A, 7B show an energy absorber according to a further
exemplary embodiment of the present invention. This structure is
designated by a slim design. Here, the individual energy absorber
elements 1, 2, 3, 4, 9, 10 are connected to one another via a
central tension rod 701. The differently positioned sheets may
affect a favorable force distribution on the cover layers 101, 102
through the now existing three force lines 1181, 1182, 1183.
[0088] FIGS. 8A through 9D show an energy absorber with an
adjustment element according to a further exemplary embodiment of
the present invention. The force progression may be adjusted freely
by continuous change of the cover sheet distance. This adjustment
element system may be used for the single decker principle as well
as for the double or multiple decker principle.
[0089] The adjustment element system includes a first adjustment
element 801, a second adjustment element 802, and a cover sheet
803, which may be displaced by actuation of both adjustment
elements 801, 802.
[0090] By actuation of the adjustment elements 801, 802, the cover
sheet 803 can be displaced, such that the energy absorber element 1
is squeezed together more or less intensely.
[0091] In the configuration shown in FIGS. 8A, 8B, the uniform,
substantially constant force-path-progression of FIG. 8C may be
provided.
[0092] In the position shown in FIG. 8D (here the adjustment
elements 801, 802 are screwed in more strongly, so that the cover
sheet 803 presses together the energy absorber element 1 more
strongly), the force-path-progression shown in FIG. 8D may be
provided (at higher level than in FIG. 8C).
[0093] In the position shown in FIG. 9A, in which the cover sheet
803 is positioned inclined, the force progression shown in FIG. 9B
may be provided. Here, after expenditure of a minimal force, the
force progression is not constant, rather decreases upon pulling
out of the strip 1. On the contrary, the force progression
increases upon pushing in of the strip.
[0094] The cover sheet 803 also may have a different form, for
example, a hump or bulge 808, which leads to bending of the sheet 1
still further in the region 809, thereby changing the
force-path-progression accordingly.
[0095] In the configuration shown in FIG. 9C, a reverse force
progression (see FIG. 9D) is provided, in which upon pulling out of
the sheet 1, the force expended therefore increases (and vice
versa).
[0096] FIGS. 10A through 11D show a double decker system with
adjustment elements 801, 802, 805, 806 and cover sheets 803,
807.
[0097] The force progression resulting from the configuration of
FIGS. 10A, 10B is shown in FIG. 10C. The force progress constantly
here upon pulling out or pushing in of the sheet 1, 3.
[0098] If the adjustment elements 801, 802, 805, 806 are screwed in
(see FIG. 10D), an increased force progression is provided (see
FIG. 10E).
[0099] If the adjustment elements are screwed in strongly in a
different manner, as shown in FIG. 11A, a force progression that
decreases upon pulling out is provided (see FIG. 11B).
[0100] If in contrast the adjustment elements are screwed opposite
to the configuration of FIG. 11A (see FIG. 11C), an increased force
progression is provided upon pulling out of the strip 1, 2 (see
FIG. 11D).
[0101] The adjustment elements may be positioned also via hydraulic
tappet rods, eccentric disks or electric adjustment drive instead
of by screws (see FIGS. 11A and 11C).
[0102] Thus, the force level of the absorption may be adjusted also
very quickly and/or by automation to the individual situation.
[0103] Naturally, also the use of other materials may be possible,
for example flexible, deformable plastics or other flexible,
deformable materials/material mixtures.
[0104] The shown energy absorber may also be used as an energy
absorber in so-called tie-rods. Further applications are, for
example:
[0105] Energy absorber in tie rods of hatrack chains. The
particular effect is the transfer of forces of the released holders
onto the hatrack arranged in front of it and therewith a redundancy
potential of this retaining concept. Essentially, these principles
may be useable where a permanent, positive force-fit connection
(defined kinematically) is required.
[0106] Energy absorber in undercarriages.
[0107] Energy absorber with belt systems.
[0108] Energy absorber in rudder linkage for large landing flaps
and rudders.
[0109] Energy absorber for seats.
[0110] Energy absorber with the securing of freight.
[0111] Integration of energy absorbers in the attachment points of
monuments of the cabin.
[0112] Energy absorber for APUs, in particular for attachment of
the APU ("Auxiliary Power Unit").
[0113] Energy absorber for separating walls or aircraft arrester
nets.
[0114] By changing the geometry of the absorber elements, the
bending radius and the material properties, the force levels may be
varied. In addition, the force level is adjustable by changing
spacing of the cover plates. A permanent frictional connection
exists. The system may be unsusceptible to environmental
conditions. In addition, the system may be insensitive to diagonal
pull (that is, for example, diagonal with reference to the arrow in
FIG. 9A), which can occur for example with a crash by deformation
of the primary structure. Here, a relative displacement of
elements/components can occur, which may have as a result a
deviation in the pullout direction.
* * * * *